Airplane control



Aug, 13, 1940. J. N. HESS AIRPLANE CONTROL Fi led se t. 7, 19.59

2,ii,6i

2,211,267 LANE CONTROL Jesse N. Hess, Pampa, Tex. Application September 7, 1939, Serial No. 293,821

1 Claim.

This invention relates to airplane controls, and has for the primary object the provision of means which may be easily adapted to an airplane and connected to the ailerons thereof for automatically actuating the latter to stabilize the airplane when encountering rough flying conditions tending to cause the airplaneto tip from side to side.

With theseand other objects in view, the invention consists in certain novel features of construction, combination and arrangement of parts fully described and the character 6 and are equipped with ailerons 1 hinged to the wings, as shown at 8. An airplane when encountering rough flying conditions has a tendency to suddenly tip from side to side and frequently if not stabilized will get out of control and enter a spin endangering the airplane and its occupants. To counteract these dangers and to automatically stabilize the airplane under these flying conditions controls'8 are adapted to the wings as clearly shown in Figure 2 and operatively connected to the ailerons. As the controls are identical in construction, a detail description will be hereinafter given of one of said controls which will be applicable to both of the controls.

The frame construction cated' by the character l0 and includes longitudinally extending members II and transverse members l2. The control is shown as mounted on one of the longitudinally extending members I i and consists of a pivotally mounted weight I3 of the wing is indiconnected to a pivotally mounted segmental gear weight I 3 as well as I by a connecting link IS. The gear I4 is pivotally mounted on the member ii of the frame and the link I5 has pivotal connection with the with the gear M. A shaft having a gear I6 is journalled on the member II with the gear in mesh with the segmental gear M. The shaft further includes a drum I! on which is wound a cable l8. The cable feeds off of the drum in opposite directions and passesover pulleys l9 supported by brackets 20 mounted on the member ll of the frame. One end. of the cable is connected to an upstanding arm 2| secured on the aileron 1 while the other end of the cable is connected to a depending arm 22 secured on the aileron. When the wing is in a horizontal position the aileron is maintained in. a plane with the plane of the wing by the weight l3. However, when the wing tips, the weight swings in the direction of the lowering of the wing and brings about movement of the aileron out of the plane of the wing to counteract the tipping of the wing and thereby bring about stabilizing of the airplane when encountering rough flying condition.

The control as shown in the scribed in detail consists of a of parts and may be readily installed on the frame of a wing within the walls of the wing and will effectively stabilize an airplane under the most severe flying conditions.

It is believed that the foregoing description, when takenin connection with the drawingwill fully set forth the construction and advantages of the invention to those skilled in the art to drawing and def minimumnumber which such a device relates, so that further detailed description will not be required.

Having thus described the invention, what I claim is: V

In combination with an airplane wing including a frame construction and upper and lower wall construction for said frame and defining a" closed space within the wing, an aileron hinged on said wing and having oppositely extending arms, a shaft journaled in the frame within said closed space, a drum secured on said shaft, pulleys mounted on said frame at opposite sides of 

